8x6E (8x6E.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 0.8000 6.0000 0.0000 0.0000 0.4000 0.0000 0.3834 0.0000 0.3067 0.0000 0.1100 0.0000 0.0000 0.0950 0.7624 6.0000 0.0092 -0.3313 0.3950 0.0047 0.3570 0.8791 0.2722 0.2118 0.1116 0.0116 -0.0493 0.1900 0.7115 6.0000 0.0735 -0.6567 0.3898 0.0177 0.3320 3.5242 0.2362 0.2009 0.1164 0.0326 -0.0486 0.2850 0.6560 6.0000 0.2527 -0.9059 0.3850 0.0379 0.3084 8.0320 0.2023 0.1837 0.1236 0.0585 -0.0458 0.3800 0.6056 6.0000 0.6147 -0.9232 0.3810 0.0640 0.2861 14.4386 0.1732 0.1572 0.1323 0.0871 -0.0390 0.4750 0.5699 6.0000 1.2302 -0.5576 0.3782 0.0943 0.2651 22.4007 0.1511 0.1281 0.1437 0.1158 -0.0285 0.5700 0.5556 6.0000 2.1457 0.3220 0.3771 0.1277 0.2454 30.9270 0.1363 0.1010 0.1592 0.1420 -0.0141 0.6650 0.5644 6.0000 3.3263 1.7373 0.3781 0.1625 0.2270 38.5231 0.1281 0.0791 0.1799 0.1634 0.0042 0.7600 0.5928 6.0000 4.5838 3.4121 0.3815 0.1973 0.2100 43.8281 0.1245 0.0636 0.2058 0.1777 0.0265 0.8550 0.6355 6.0000 5.5807 4.7700 0.3878 0.2307 0.1944 46.0911 0.1235 0.0551 0.2351 0.1828 0.0520 0.9500 0.6900 6.0000 5.9965 5.3838 0.3974 0.2613 0.1800 45.1317 0.1242 0.0546 0.2650 0.1758 0.0782 1.0450 0.7484 6.0000 6.0000 5.4659 0.4085 0.2847 0.1670 42.4213 0.1250 0.0593 0.2892 0.1598 0.0989 1.1400 0.7984 6.0000 6.0000 5.5397 0.4179 0.2958 0.1553 39.9515 0.1240 0.0626 0.3014 0.1448 0.1100 1.2350 0.8401 6.0000 6.0000 5.6080 0.4259 0.2959 0.1449 37.7120 0.1218 0.0647 0.3027 0.1309 0.1121 1.3300 0.8740 6.0000 6.0000 5.6691 0.4323 0.2932 0.1359 35.6781 0.1188 0.0659 0.3012 0.1182 0.1127 1.4250 0.9006 6.0000 6.0000 5.7219 0.4372 0.2892 0.1282 33.8271 0.1154 0.0663 0.2986 0.1068 0.1133 1.5200 0.9201 6.0000 6.0000 5.7656 0.4407 0.2840 0.1218 32.1388 0.1121 0.0663 0.2949 0.0967 0.1136 1.6150 0.9331 6.0000 6.0000 5.7994 0.4429 0.2779 0.1168 30.5953 0.1090 0.0659 0.2902 0.0879 0.1134 1.7100 0.9400 6.0000 6.0000 5.8224 0.4437 0.2707 0.1131 29.1807 0.1063 0.0655 0.2846 0.0804 0.1127 1.8050 0.9411 6.0000 6.0000 5.8345 0.4433 0.2626 0.1107 27.8809 0.1042 0.0650 0.2781 0.0742 0.1114 1.9000 0.9368 6.0000 6.0000 5.8365 0.4417 0.2537 0.1094 26.6839 0.1025 0.0645 0.2707 0.0693 0.1095 1.9950 0.9277 6.0000 6.0000 5.8354 0.4388 0.2441 0.1084 25.5786 0.1006 0.0636 0.2625 0.0655 0.1070 2.0900 0.9140 6.0000 6.0000 5.8327 0.4349 0.2339 0.1074 24.5559 0.0982 0.0621 0.2537 0.0626 0.1039 2.1850 0.8962 6.0000 6.0000 5.8292 0.4299 0.2232 0.1065 23.6072 0.0955 0.0601 0.2441 0.0607 0.1004 2.2800 0.8748 6.0000 6.0000 5.8228 0.4239 0.2122 0.1057 22.7253 0.0924 0.0576 0.2340 0.0597 0.0965 2.3750 0.8500 6.0000 6.0000 5.8152 0.4169 0.2009 0.1049 21.9039 0.0891 0.0548 0.2234 0.0595 0.0922 2.4700 0.8225 6.0000 6.0000 5.8072 0.4090 0.1893 0.1041 21.1371 0.0856 0.0517 0.2124 0.0599 0.0876 2.5650 0.7924 6.0000 6.0000 5.7994 0.4002 0.1775 0.1034 20.4199 0.0820 0.0483 0.2009 0.0609 0.0827 2.6600 0.7603 6.0000 6.0000 5.7918 0.3906 0.1657 0.1028 19.7479 0.0782 0.0448 0.1891 0.0623 0.0775 2.7550 0.7266 6.0000 6.0000 5.7849 0.3802 0.1537 0.1022 19.1172 0.0743 0.0412 0.1770 0.0641 0.0720 2.8500 0.6916 6.0000 6.0000 5.7774 0.3691 0.1417 0.1017 18.5241 0.0703 0.0376 0.1647 0.0662 0.0663 2.9450 0.6559 6.0000 6.0000 5.7710 0.3573 0.1297 0.1013 17.9655 0.0664 0.0340 0.1522 0.0683 0.0604 3.0400 0.6197 6.0000 6.0000 5.7659 0.3449 0.1177 0.1009 17.4386 0.0625 0.0305 0.1396 0.0702 0.0542 3.1350 0.5836 6.0000 6.0000 5.7630 0.3319 0.1058 0.1005 16.9409 0.0587 0.0271 0.1269 0.0719 0.0478 3.2300 0.5479 6.0000 6.0000 5.7622 0.3184 0.0940 0.1002 16.4700 0.0549 0.0240 0.1143 0.0731 0.0413 3.3250 0.5130 6.0000 6.0000 5.7614 0.3045 0.0824 0.1000 16.0239 0.0513 0.0211 0.1017 0.0737 0.0344 3.4200 0.4794 6.0000 6.0000 5.7550 0.2900 0.0710 0.0998 15.6008 0.0479 0.0185 0.0890 0.0736 0.0271 3.5150 0.4475 6.0000 6.0000 5.7397 0.2753 0.0597 0.0997 15.1989 0.0446 0.0161 0.0763 0.0724 0.0193 3.6100 0.4176 6.0000 6.0000 5.7141 0.2601 0.0486 0.0997 14.8167 0.0416 0.0141 0.0638 0.0701 0.0111 3.7050 0.3902 6.0000 6.0000 5.6751 0.2448 0.0379 0.0997 14.4529 0.0389 0.0123 0.0515 0.0665 0.0026 3.7961 0.3615 6.0000 6.0000 5.5676 0.2248 0.0266 0.0997 14.1201 0.0360 0.0106 0.0385 0.0591 -0.0065 3.8202 0.3492 6.0000 6.0000 5.5085 0.2145 0.0224 0.0997 14.0345 0.0348 0.0099 0.0338 0.0542 -0.0097 3.8404 0.3367 6.0000 6.0000 5.4657 0.2035 0.0183 0.0998 13.9636 0.0336 0.0093 0.0292 0.0488 -0.0128 3.8606 0.3219 6.0000 6.0000 5.4309 0.1901 0.0137 0.0998 13.8934 0.0321 0.0085 0.0239 0.0420 -0.0162 3.8808 0.3041 6.0000 6.0000 5.4024 0.1737 0.0084 0.0998 13.8238 0.0304 0.0076 0.0179 0.0335 -0.0200 3.9010 0.2827 6.0000 6.0000 5.3851 0.1535 0.0022 0.0998 13.7550 0.0282 0.0066 0.0109 0.0229 -0.0244 3.9212 0.2559 6.0000 6.0000 5.3891 0.1280 -0.0052 0.0999 13.6868 0.0256 0.0054 0.0025 0.0094 -0.0295 3.9414 0.2205 6.0000 6.0000 5.4422 0.0938 -0.0146 0.0999 13.6192 0.0220 0.0040 -0.0081 -0.0089 -0.0358 3.9616 0.1632 6.0000 6.0000 5.6841 0.0383 -0.0291 0.0999 13.5524 0.0163 0.0022 -0.0244 -0.0386 -0.0451 3.9818 0.0858 6.0000 6.0000 6.3977 -0.0371 -0.0483 0.1000 13.4861 0.0086 0.0006 -0.0458 -0.0790 -0.0571 4.0000 0.0163 6.0000 6.0030 6.0030 -0.1049 -0.0652 0.1000 13.4336 0.0016 0.0000 -0.0652 0.0000 0.0000 RADIUS: 4.00 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 0.95 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.031693 TOTAL WEIGHT (Kg) = 0.014373 TOTAL VOLUME (IN**3) = 0.516324 TOTAL PROJECTED AREA (IN**2) = 4.9478 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000214 MOMENT OF INERTIA (Kg-M**2) = 0.000024 STATIC MOMENT, ONE SIDE (IN-LB) = 0.019812 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 107.864 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 20003.15 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.95, E63 (Transition Start, Airfoil 1) AIRFOIL2: 3.36, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412